US20190118925A1 - Aircraft Fuselage Comprising At Least Two Transparent Walls Interposed Between An Upper Portion And A Lower Portion Of The Fuselage - Google Patents
Aircraft Fuselage Comprising At Least Two Transparent Walls Interposed Between An Upper Portion And A Lower Portion Of The Fuselage Download PDFInfo
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- US20190118925A1 US20190118925A1 US16/149,427 US201816149427A US2019118925A1 US 20190118925 A1 US20190118925 A1 US 20190118925A1 US 201816149427 A US201816149427 A US 201816149427A US 2019118925 A1 US2019118925 A1 US 2019118925A1
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- edge
- fuselage
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- 238000005304 joining Methods 0.000 claims abstract description 15
- 238000009432 framing Methods 0.000 claims description 18
- 230000000873 masking effect Effects 0.000 claims description 7
- 239000012788 optical film Substances 0.000 claims description 3
- 230000002787 reinforcement Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920000515 polycarbonate Polymers 0.000 description 1
- 239000004417 polycarbonate Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cage And Drive Apparatuses For Elevators (AREA)
- Body Structure For Vehicles (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
- The present application relates to an aircraft fuselage comprising at least two transparent walls interposed between an upper portion and a lower portion of the fuselage.
- As illustrated in
FIG. 1 , anaircraft 10 comprises afuselage 12 which extends from a nose 12.1 to a tail 12.2, and twowings 14 disposed on either side of thefuselage 12. - In the remainder of the description, a longitudinal direction DL is parallel to the longitudinal axis of the fuselage which extends from the nose 12.1 to the tail 12.2. A transverse plane is perpendicular to the longitudinal direction DL.
- In one manufacturing technique, the
fuselage 12 is made up of a plurality ofportions 16 that are disposed end-to-end and connected together. - According to an embodiment visible in
FIGS. 3 and 4 , eachportion 16 comprises: -
- a
framework 18 which hasframes 20 positioned in transverse planes and stringers 22 oriented in the longitudinal direction DL, and - a skin 24 secured to the
framework 18.
- a
- Each
frame 20 is in the form of a ring which extends around the entire circumference of thefuselage 12. Theframes 20 are spaced apart regularly along thefuselage 12. They notably react the forces brought about on the skin 24 of the fuselage in flight by the difference in pressure between the interior and exterior of the fuselage. -
Certain frames 20′ are reinforced and are positioned at locations where the forces are significant, for example in the joining zones in which thewings 14 and the empennage are joined to thefuselage 12. -
Certain stringers 22′ are reinforced and referred to as spars. - The skin 24 generally comprises a plurality of juxtaposed panels.
- In order to allow light to pass into the interior of the fuselage and the passengers to see the external environment, the skin 24 comprises
portholes 26 which are generally aligned along two lateral generatrices that are positioned at the level of the headrests of the seats of the passenger cabin. - In an embodiment illustrated in
FIG. 4 , eachporthole 26 comprises atransparent wall 28, asurround 30 which supports thetransparent wall 28 and which is positioned between twosuccessive frames 20 and twosuccessive stringers 22. - With each surround 30 being spaced apart from the
frames 20 and thestringers 22, the skin 24 is reinforced around thesurround 30 in order to ensure the transmission of forces between thesurround 30 and theframework 18. - Since the
portholes 26 have to be disposed between twosuccessive frames 20 and twosuccessive stringers 22, they have small dimensions. - Aspects of the present invention may remedy the drawbacks of the prior art.
- An embodiment of the invention is an aircraft fuselage comprising a passenger cabin equipped with seats, characterized in that the fuselage comprises:
-
- at least one lower part which has a right-hand upper edge and a left-hand upper edge,
- at least one upper part which has a right-hand lower edge connected to the right-hand upper edge of the lower part in a first joining zone and a left-hand lower edge connected to the left-hand upper edge of the lower part in a second joining zone,
- structural connections connecting the lower part and the upper part,
- in each first and second joining zone, at least one space between the lower and upper parts and the structural connections, and
- a transparent wall for closing off each space.
- An aspect of the invention makes it possible to obtain much larger transparent walls.
- According to another feature, the first and second joining zones are positioned above the seats of the passenger cabin.
- According to other features:
-
- the lower part comprises a lower framework, having lower frames disposed in transverse planes distributed regularly in a longitudinal direction, and a lower skin secured to the lower framework,
- the upper part comprises an upper framework, having upper frames disposed in transverse planes distributed regularly in the longitudinal direction, and an upper skin secured to the upper framework, and
- certain lower frames of the lower part are reinforced and positioned in line with reinforced upper frames of the upper part, the reinforced lower frames each comprising a first end connected to a first end of one of the reinforced upper frames by a first connection, and a second end connected to a second end of the reinforced upper frame by a second connection, a reinforced lower frame and a reinforced upper frame connected by the first and second connections forming a structural connection.
- According to other features:
-
- the lower skin has a right-hand upper edge face and a left-hand upper edge face,
- the upper skin has a right-hand lower edge face and a left-hand lower edge face,
- the right-hand upper edge face and left-hand upper edge face, respectively, of the lower skin and the right-hand lower edge face and left-hand lower edge face, respectively, of the upper skin are spaced apart between the structural connections and joined at the structural connections.
- According to a first embodiment, for each space, the fuselage comprises a framing structure which has two spars connecting the structural connections when the framing structure is mounted and two uprights connecting the spars, the transparent wall being mounted edge-to-edge on the framing structure.
- The framing structure may comprise at least one reinforcement, parallel to the uprights, connecting the spars.
- In a second embodiment, (i) at least some of the lower frames interposed between the reinforced lower frames and at least some of the upper frames interposed between the reinforced upper frames and disposed in line with the lower frames pass through each space, (ii) the lower part comprises at least one lower spar which connects two structural connections, (iii) the upper part comprises at least one upper spar which connects two structural connections, (iv) the transparent wall is mounted edge-to-edge on a surround, formed by the lower and upper spars and the structural connections, and is supported by the upper and lower frames.
- According to another feature, each transparent wall is equipped with a masking system configured to opacify the transparent wall in an activated state.
- According to one embodiment, the masking system comprises an electrochromatic or electro-optical film which is attached to the transparent wall.
- A further subject of the invention is an aircraft comprising a fuselage according to the invention.
- Further features and advantages will become apparent from the following description of the invention, said description being given only by way of example, with reference to the appended drawings, in which:
-
FIG. 1 is a perspective view of an aircraft, -
FIG. 2 is a perspective view of portions of an aircraft fuselage, which illustrates one embodiment of the prior art, -
FIG. 3 is a perspective view of a part of a portion of an aircraft fuselage, which illustrates one embodiment of the prior art, -
FIG. 4 is a perspective view of a part of a portion of an aircraft fuselage incorporating portholes, which illustrates one embodiment of the prior art, -
FIG. 5 is a top view of an aircraft fuselage, which illustrates one embodiment of the invention, -
FIG. 6 is a top view of a part of an aircraft fuselage, which illustrates one embodiment of the invention, -
FIG. 7 is a cross section on the line VII-VII of the fuselage visible inFIG. 5 , -
FIG. 8 is a cross section on the line VIII-VIII of the fuselage visible inFIG. 5 , -
FIG. 9 is a diagram of a part of an aircraft fuselage, which illustrates a first embodiment of the invention, and -
FIG. 10 is a diagram of a part of an aircraft fuselage, which illustrates a second embodiment of the invention. -
FIGS. 5, 7 and 8 show anaircraft fuselage 32 which has an approximately circular section in a transverse plane. However, the invention is in no way limited to this type of section. Thus, the fuselage can have an oblong shape with a large vertical dimension or a large horizontal dimension. - The aircraft comprises a
horizontal floor 34 connected to thefuselage 32, thefuselage 32 and thefloor 34 delimiting, in the upper part, a passenger cabin 36, inter alia. - The passenger cabin 36 comprises
seats 38 that are arranged in a number of rows. In a configuration that is visible inFIG. 8 , theseats 38 are separated by twoaisles 40 that are parallel to the longitudinal direction DL and symmetric with respect to a vertical midplane PMV (which corresponds to the vertical plane passing through the longitudinal axis). However, this configuration does not limit the invention, which can also be based on a configuration having a single aisle or a greater number of aisles. - The
fuselage 32 extends from a nose 32.1 to a tail 32.2 and comprises at least onelower part 42, which has a right-hand upper edge 42.1 and a left-hand upper edge 42.2, and at least oneupper part 44 which has a right-hand lower edge 44.1 connected to the right-hand upper edge 42.1 of thelower part 42 in a first joining zone 46, and a left-hand lower edge 44.2 connected to the left-hand upper edge 42.2 of thelower part 42 in a second joiningzone 48. - The right-hand and left-hand upper edges 42.1 and 42.2 of the
lower part 42 of the fuselage each comprise a rectilinear portion that is oriented parallel to the longitudinal direction DL, front ends that are separated or converge towards a front point 42.3, and/or rear ends that are separated or converge towards a rear point 42.4. - The right-hand and left-hand upper edges 42.1 and 42.2 are substantially symmetric with respect to the vertical midplane PMV.
- The right-hand and left-hand lower edges 44.1 and 44.2 of the
upper part 44 of the fuselage each comprise a rectilinear portion that is oriented parallel to the longitudinal direction DL, front ends that are separated or converge towards a front point 44.3, and/or rear ends that are separated or converge towards a rear point 44.4. - The right-hand and left-hand lower edges 44.1 and 44.2 are substantially symmetric with respect to the vertical midplane PMV.
- The
lower part 42 extends around more than half the circumference of thefuselage 32, such that the first and second joiningzones 46, 48 are positioned above theseats 38 of the passenger cabin 36. In one configuration, the first and second joiningzones 46, 48 are positioned above and vertically in line with theaisles 40 of the passenger cabin 36. - The
lower part 42 comprises a lower framework 50 to which alower skin 52 formed by juxtaposed panels is secured. - The lower framework 50 comprises
lower stringers 54 andlower frames 56 that are disposed in transverse planes distributed regularly in the longitudinal direction DL. The lower frames 56 extend around only a part of the circumference, between the right-hand and left-hand upper edges 42.1 and 42.2 of thelower part 42 when they are positioned in transverse planes which intersect the right-hand and left-hand upper edges 42.1 and 42.2 of thelower part 42. Lower frames 56 can extend around the entire circumference of thefuselage 32 when they are positioned in transverse planes which do not intersect the right-hand and left-hand upper edges 42.1 and 42.2 of thelower part 42. - The
lower stringers 54 and thelower frames 56 are distributed and dimensioned notably so as to react forces brought about on thelower skin 52 of thelower part 42 in flight by the difference in pressure between the interior and the exterior of the fuselage. - The
upper part 44 comprises anupper framework 58 to which anupper skin 60 is secured. - The
upper framework 58 comprises upper stringers 62 andupper frames 64 that are disposed in transverse planes distributed regularly in the longitudinal direction DL. Theupper frames 64 extend around only a part of the circumference, between the right-hand and left-hand lower edges 44.1 and 44.2 of theupper part 44. - The upper stringers 62 and the
upper frames 64 are distributed and dimensioned notably so as to react forces brought about on theupper skin 60 of theupper part 44 in flight by the difference in pressure between the interior and the exterior of the fuselage. - The upper and
lower frameworks 50, 58 and the lower andupper skins upper skins - According to the invention, the
lower part 42 and theupper part 44 are connected bystructural connections 66. - In one embodiment, certain
lower frames 56′ of thelower part 42 are reinforced and positioned in line with reinforcedupper frames 64′ of theupper part 44. The reinforcedlower frames 56′ each comprise a first end 56.1′ connected to a first end 64.1′ of one of the reinforcedupper frames 64′ by afirst connection 68, and a second end 56.2′ connected to a second end 64.2′ of the reinforcedupper frame 64′ by asecond connection 70. - Each first and
second connection - A reinforced
lower frame 56′ and a reinforcedupper frame 64′ that are connected by the first andsecond connections structural connection 66. - The number, distribution and dimensioning of the
structural connections 66 are determined so as to ensure the transmission of forces between the lower andupper parts - The
fuselage 32 comprises at least onespace 72, in each joiningzone 46, 48, between the lower andupper parts structural connections 66, and atransparent wall 74 for closing off eachspace 72. Thus, thetransparent walls 74 are positioned above theseats 38, notably above and vertically in line with theaisles 40 of the passenger cabin 36. - To this end, the right-hand upper edge face C52.1 (and left-hand upper edge face C52.2, respectively) of the
lower skin 52 and the right-hand lower edge face C60.1 (and left-hand lower edge face C60.2, respectively) of theupper skin 60 are spaced apart between thestructural connections 66. The right-hand upper edge face C52.1 (and left-hand upper edge face C52.2, respectively) of thelower skin 52 and the right-hand lower edge face C60.1 (and left-hand lower edge face C60.2, respectively) of theupper skin 60 are joined at thestructural connections 66, as illustrated inFIGS. 5 and 6 . - Depending on the geometry of the lower and
upper parts lower skin 52 and the right-hand and left-hand lower edge faces C60.1, C60.2 of theupper skin 60 can be rectilinear, curved or follow a profile including a combination of rectilinear and/or curved portions. In one configuration, the right-hand upper edge face C52.1 (and left-hand upper edge face C52.2, respectively) of thelower skin 52 and the right-hand lower edge face C60.1 (and left-hand lower edge face C60.2, respectively) of theupper skin 60 are parallel. - In a first embodiment that is visible in
FIG. 9 , thespace 72 is free of any structural part of thefuselage 32. Thus, thelower frames 56 interposed between the reinforcedlower frames 56′ do not extend beyond the right-hand and left-hand upper edge faces C52.1 and C52.2 of thelower skin 52, and theupper frames 64 interposed between the reinforcedupper frames 64′ do not extend beyond the right-hand and left-hand lower edge faces C60.1 and C60.2 of theupper skin 60. - In this first embodiment, for each
space 72, thefuselage 32 comprises a framing structure 76 which comprises twoparallel spars uprights spars - The
spars uprights structural connections 66. Thus, thespars structural connections 66 when the framing structure 76 is mounted. - When the framing structure 76 is mounted, the
lower frames 56 interposed between the reinforcedlower frames 56′ and theupper frames 64 interposed between the reinforcedupper frames 64′ are connected to the framing structure 76. - The framing structure 76 may comprise at least one
reinforcement 82 parallel to theuprights uprights spars - The
transparent wall 74 is mounted edge-to-edge on the framing structure 76. - In a second embodiment that is visible in
FIG. 10 , at least some of thelower frames 56 interposed between the reinforcedlower frames 56′ and at least some of theupper frames 64 interposed between the reinforcedupper frames 64′ and disposed in line with thelower frames 56 pass through eachspace 72. - In this second embodiment, the
lower part 42 comprises, at the right-hand and left-hand upper edge faces C52.1 and C52.2, at least oneupper spar 84 which connects twostructural connections 66. In one configuration, thelower part 42 comprises, at the right-hand and left-hand upper edge faces C52.1 and C52.2, anupper spar 84 between each pair ofstructural connections 66. - The
upper part 44 comprises, at the right-hand and left-hand lower edge faces C60.1 and C60.2, at least onelower spar 84′ which connects twostructural connections 66. In one configuration, theupper part 44 comprises, at the right-hand and left-hand upper edge faces C60.1 and C60.2, alower spar 84′ between each pair ofstructural connections 66. - The upper and
lower spars lower frames 56 and theupper frames 64, which are connected to said upper andlower spars - The
transparent wall 74 is mounted edge-to-edge on the surround 86 formed by the lower andupper spars structural connections 66, and is supported by the upper andlower frames - The
transparent wall 74 can be made in one piece or be made up of several juxtaposed sheets. - Each
transparent wall 74 is made for example of glass or polycarbonate. Each of said transparent walls can be equipped with a masking system configured to opacify thetransparent wall 74 in an activated state. Each masking system is actuable remotely. - In one embodiment, the masking system comprises an electrochromatic or electro-optical film which is attached to the
transparent wall 74 and which can be controlled by applying an electrical voltage to its terminals. - In one assembly technique, each lower and
upper part - In a first assembly method, the lower and
upper parts lower parts second connections transparent walls 74 are fitted at thespaces 72. - In a second assembly method, each portion of the
lower part 42 is assembled with the corresponding portion of theupper part 44 by virtue of the first andsecond connections transparent walls 74 are fitted at thespaces 72. - The invention makes it possible to obtain wider transparent walls that are positioned above the passengers' heads.
- The invention is not limited to the above-described embodiments. Thus, it is possible for the lower and
upper parts - While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1760071A FR3072645B1 (en) | 2017-10-25 | 2017-10-25 | AIRCRAFT FUSELAGE INCLUDING AT LEAST TWO TRANSPARENT WALLS INTERIED BETWEEN TWO UPPER AND LOWER PORTIONS OF THE FUSELAGE |
FR1760071 | 2017-10-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
US20190118925A1 true US20190118925A1 (en) | 2019-04-25 |
US11167834B2 US11167834B2 (en) | 2021-11-09 |
Family
ID=60627876
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US16/149,427 Active 2040-02-24 US11167834B2 (en) | 2017-10-25 | 2018-10-02 | Aircraft fuselage comprising at least two transparent walls interposed between an upper portion and a lower portion of the fuselage |
Country Status (2)
Country | Link |
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US (1) | US11167834B2 (en) |
FR (1) | FR3072645B1 (en) |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB439645A (en) * | 1934-06-27 | 1935-12-11 | Petters Ltd | Improvements in and relating to windshield devices for cockpits of aircraft or for equivalent spaces in other vehicles |
US2701899A (en) * | 1948-06-26 | 1955-02-15 | Goodrich Co B F | Inflatable sealing strip |
US2680582A (en) * | 1951-05-08 | 1954-06-08 | Northrop Aircraft Inc | Canopy attachment |
DE20118717U1 (en) * | 2001-11-16 | 2002-02-21 | Chen Ching Chang | Airplane with a panoramic view |
US7530531B2 (en) * | 2004-10-04 | 2009-05-12 | The Boeing Company | Apparatus and methods for installing an aircraft window panel |
US7823832B2 (en) * | 2004-10-04 | 2010-11-02 | The Boeing Company | Injection-molded window panel and related methods |
US8939406B2 (en) * | 2012-07-02 | 2015-01-27 | The Boeing Company | Joining composite fuselage sections along window belts |
US9561853B2 (en) * | 2013-05-17 | 2017-02-07 | Honda Patents & Technologies North America, Llc | Window of an aircraft |
US9708065B2 (en) * | 2015-04-07 | 2017-07-18 | The Boeing Company | Crown cabin configuration for an aircraft |
US10214276B2 (en) * | 2015-04-14 | 2019-02-26 | Shakil Hussain | Aircraft external viewing system, apparatus, and method |
-
2017
- 2017-10-25 FR FR1760071A patent/FR3072645B1/en active Active
-
2018
- 2018-10-02 US US16/149,427 patent/US11167834B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3072645A1 (en) | 2019-04-26 |
US11167834B2 (en) | 2021-11-09 |
FR3072645B1 (en) | 2021-12-17 |
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